The heat transfer and characteristics of the fluid flow in the duct of the trailing edge of the turbine blade with parted pin-fin arrays were experimentally investigated.
本文对具有断裂结构扰流柱的涡轮叶片尾缘楔型通道的流动与换热过程进行了实验研究。
The computations show that the droplets distribution, entropy increase, wetness fraction, and flow angle are changed when the shape of trailing edge varies.
结果显示，出气边形状的改变影响凝结流中水滴状态、熵增、湿度、出口气流角的分布。
In this paper, heat transfer and fluid flow in passage for trailing edge of turbine blade with pin-fin arrays is studied numerically.
本文应用湍流模型对涡轮叶片尾缘针肋通道的换热与流动进行了二维数值模拟研究。
Looking at that in the lab, it becomes a function of airfoil shape, and also of the flow control technologies you use to enhance the laminar flow with conformal trailing edge surfaces.
实验室的研究表明，它已经成了机翼的一项功能，也是通过适形机翼后缘表面来增强层流的流控制技术的功能。
The ejection from the half slot only blows away the vortex on the slot surface, and has little effect on the flow field near the trailing edge.
半开缝时，喷气的引入仅吹除了附着在开缝处的漩涡，对于尾缘处流场影响不大。
The heat transfer and characteristics of the fluid flow in the duct with waist-shaped pin - fin arrays for the trailing edge of the turbine blade were experimentally investigated.
本文对涡轮叶片尾缘中具有束腰结构扰流柱的冷却通道的传热和流动阻力特性进行了实验研究，重点研究了雷诺数、扰流柱的束腰比以及不同组合的影响。
Airfoil trailing-edge vortex separation occurs, resulting in movement of the flow field near the airfoil stall.
翼型后缘出现的分离涡，导致翼型附近流场的流动失速。
And the viscous separation flow of wing-body trailing edge conjunction can be effectively simulated. Therefore these algorithms are valuable for the engineering applications.
计算结果与风洞实验的对比表明，文中所采用的数值方法可以有效的模拟翼身结合处粘性分离流动，具有一定的工程实用价值。
And the viscous separation flow of wing-body trailing edge conjunction can be effectively simulated. Therefore these algorithms are valuable for the engineering applications.
计算结果与风洞实验的对比表明，文中所采用的数值方法可以有效的模拟翼身结合处粘性分离流动，具有一定的工程实用价值。
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